Memorandum presenting the effects of wing modification and stability augmentation on the computed longitudinal behavior in the pitch-up region and probable pilot opinion of the pitch-up characteristics of two current fighter airplanes. An exploration of the addition of a wing-leading edge is included. Results regarding computed pitch-up behavior and probable pilot opinion are provided.

Report presenting an investigation to determine the effects on the static longitudinal and lateral stability characteristics of a model with a swept wing of aspect ratio 3, horizontal-tail height and dihedral, and a ventral fin. Tests were performed at a range of angles of attack and Mach numbers.

Report presenting an investigation at Mach numbers of 1.79 to 2.67 on a wing-fuselage combination and on the wing-fuselage combination with a complete tail configuration. Two wing plan forms were investigated on the fuselage, which differed in sweepback and taper ratio.

Report presenting an exploration of some of the problems of manned orbital vehicles, which introduce many problems in the fields of escape, piloting, orbit selection, flight termination, and range requirements. The effects of some of these problems, including some effects of configuration, are discussed.

Report presenting some experimental data and calculations for a variety of aerodynamic shapes considered for use as manned reentry vehicles. Three types of vehicles were tested: non-lifting bodies, lifting bodies, and airplane-like vehicles. All of the configuration types were found to be suitable for use as manned reentry vehicles with certain fin and flap modifications for certain shapes.

Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.

Report presenting an investigation of the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination. The model had a wing of aspect ratio 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding chordwise pressure distributions, the effect of ailerons on wing section loadings, the effect of aileron on wing loading, and the effects of a deflected aileron on opposite-wing loading are presented.

Report presenting the wing-section pressure-distribution and wing-panel load characteristics of the Douglas D-558-II airplane for a range of Mach numbers and airplane normal-force coefficients. At subsonic speeds, the pressure distributions are characterized by a high negative-pressure peak with an abrupt pressure recovery as a result of the leading-edge expansion over the upper surface at moderate angles of attack.

Memorandum presenting a free-flight investigation conducted on four supersonic nose inlets. Each inlet used conical-shock and isentropic-compression center bodies; two of the models had internal contraction and two did not. Results regarding drag coefficient, pressure recovery, mass-flow ratio, and Reynolds number range are provided.

Memorandum presenting the buffet characteristics of a scale model of an attack airplane over a range of Mach numbers. The wing had a modified delta plan form with an NACA 0008 airfoil section at the root and an NACA 0005 airfoil section at the tip, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding the frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet input force are provided.

Report presenting an investigation of the buffet characteristics of a model of an attack airplane at a variety of Mach numbers. The wing had a modified delta plan form with two NACA airfoils, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet input force are provided.

Report presenting an investigation in the 16-foot transonic tunnel at a variety of Mach numbers to determine the interference effects of a hot jet exhaust on the pressure distribution of a 60 degree delta wing. Results regarding the tabulated pressure coefficients for the wing and nacelle for the complete range of test conditions are provided.

Report presenting testing of a highly polished 9-inch-diameter hemisphere-cylinder in flight in order to obtain boundary-layer transition and heat-transfer data. Results regarding the free-stream conditions, pressure measurements, temperature measurements, heat-transfer measurements, and transition and transition parameters are provided.

"The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results" (p. 1).

Report presenting an investigation of an inlet with combined external and internal supersonic compression, formed by spike and cowl oblique shocks, and an overall length of 2.5 inlet diameters at a range of Mach numbers over a range of angles of attack. With proper boundary layer control on the centerbody, this method of internal compression did not adversely affect the high performance of the inlet.

Memorandum presenting the results of experimental and theoretical data on nine cowls to determine the effect of initial lip angle and projected frontal area on the cowl pressure drag coefficient at Mach numbers from 1.90 to 3.88. Results regarding the surface pressure coefficients, pressure distributions, effect of lip angle, projected cowl area, and Mach number on the cowl pressure drag coefficients are provided.

Memorandum presenting an analysis to determine, for control design purposes, the approximate response of pressures in the ramjet engine to changes in fuel flow. In the first part, the response after dead time is treated by the linearized lumped-parameter method. In the second, the dead time occurring between the change in fuel flow and the beginning of the pressure response is discussed.

From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."

Report discussing an investigation to determine the effect of spin on the aerodynamic characteristics of the Army Ordnance Corps 60-millimeter T-24 mortar shell with several tail-fin configurations. Tests were performed at several airspeeds, speeds of rotation, and angles of attack. Under all test conditions, the models were statistically stable and the yawing moment increased with speed of rotation at higher angles of attack.

Report presenting an investigation in the high-speed tunnel to determine the effect of spin on the aerodynamic characteristics of a 60-millimeter T-24 mortar shell with several different tail-fin configurations. Tests were made at a range of airspeeds, speeds of rotation, and angles of attack. Results regarding forced-spin tests, free-spin tests, and zero-spin tests are provided.

Report presenting the basic performance characteristics of several types of designs of subsonic-diffuser-bypass-duct combinations for bypass flows up to one-third of the total flow. The tested bypass-duct design procedure was found to be greatly oversimplified and was unable to produce satisfactory performance because of the extreme adverse pressure gradient.

A modified corrugated-insert blade with integrally cast shell and base was developed. This blade was as light as a conventional fabricated corrugated-insert blade. Of four test blades operated in a full-scale turbojet engine, one failed after about 15 hours operation at an inlet gas temperature of 1670 degrees F, a coolant-flow ratio of 0.0064, and a 1/3-span centrifugal stress of approximately 28,000 psi. Three other test blades ran for approximately 16, 31, and 36 hours without failure at similar conditions.

"The performance of a 2.8 KS 8100 Cajun solid-propellant rocket motor has been determined from the free-flight test of a single-stage model which reached a velocity of 5,268 feet per second (Mach number, 4.74). Thrust data from the flight test are compared with data obtained from a ground firing test made by the manufacturer and the two are shown to be in agreement." Report presenting general drag, data, and acceleration are also provided.

Memorandum presenting an investigation in the supersonic pressure tunnel at a free-stream Mach number of 2.01 and at angles of attack up to 15 degrees of the static pressures and boundary-layer characteristics on the forward parts of nine fusleages of various cross-sectional shapes. Results regarding the static pressure distributions, boundary-layer characteristics, and selection of fuselage shapes for use with top-mounted scoop inlets are provided.